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Improved Data-Driven trajectory optimization Method Utilizing Deep trajectory Generation

JOURNAL OF AEROSPACE INFORMATION SYSTEMS 2025年第1期22卷 28-42页

作者： Gui, Xuhao Zhang, Junfeng Tang, Xinmin Bao, Jie Nanjing Univ Aeronaut & Astronaut Coll Civil Aviat Nanjing 211106 Peoples R China Civil Aviat Univ China Coll Transportat Sci & Engn Tianjin 300300 Peoples R China

The imbalance between air traffic capacity and demand, especially in the terminal maneuvering area, constrains the development of the civil aviation industry. To enhance the capacity, providing aircraft with optimal trajectories is the way forward. The key challenge of building a trajectory optimization model lies in embedding air traffic controllers' operation experience into the optimization process. Previous efforts proposed a data-driven trajectory optimization method to learn operation experience from historical data for trajectory optimization use, which is limited by the issues of insufficient quantity and diversity of trajectory data. To solve those issues, an improved model is proposed to further improve the trajectory optimization performance. Firstly, this paper exploited a connecting-based trajectory generation model to generate massive synthetic trajectories. Then, this paper used a data-mining-based valuable trajectory identification technique to find valuable trajectories that can be used to enrich its operation experience. A case study on Guangzhou Baiyun International Airport was conducted to verify the proposed method. The results show that the proposed model successfully incorporates more operation experience during the optimization process. Compared with the benchmark model, the proposed model can adapt to more complex air traffic and provide optimal trajectories for more incoming aircraft.

关键词： trajectory optimization model Terminal Manoeuvring Area Data Mining Air Traffic Controller Civil Aviation Guangzhou Baiyun International Airport Aircraft Performance Airspace Generative Adversarial Network Calibrated Airspeed

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A System-View Optimal Additional Active Power Control ofWind Turbines for Grid Frequency Support

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IEEE TRANSACTIONS ON POWER SYSTEMS 2024年第2期39卷 4323-4335页

作者： Zhang, Yubo Hao, Zhiguo Yang, Songhao Zhang, Baohui Xi An Jiao Tong Univ State Key Lab Elect Insulat & Power Equipment Xian 710049 Peoples R China

Additional active power control (AAPC) of wind turbines (WTs) is essential to improve the transient frequency stability of low-inertia power systems. Most of the existing research has focused on imitating the frequency response of the synchronous generator (SG), known as virtual inertia control (VIC), but are such control laws optimal for the power systems? Inspired by this question, this article proposes an optimal AAPC of WTs to maximize the frequency nadir post a major power deficit. By decoupling theWTresponse and the frequency dynamics, the optimal frequency trajectory is solved based on the trajectory model, and its universality is strictly proven. Then the optimal AAPC ofWTs is constructed reversely based on the average system frequency (ASF) model with the optimal frequency trajectory as the desired control results. The proposed method can significantly improve the system frequency nadir. Meanwhile, the event insensitivity makes it can be deployed based on the on-line rolling update under a hypothetic disturbance, avoiding the heavy post-event computational burden. Finally, simulation results in a two-machine power system and the IEEE 39 bus power system verify the effectiveness of the optimal AAPC of WTs.

关键词： Frequency support frequency nadir wind turbine (WT) additional active power control (AAPC) average system frequency (ASF) model trajectory optimization model

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Analytic Gradient Computation and Applications in Multitarget Multi-Impulse trajectory optimization

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2024年第2期47卷 347-357页

作者： Zhang, Nan Di, Wu Baoyin, Hexi Tsinghua Univ Sch Aerosp Engn Beijing 100084 Peoples R China

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Improved Simulated Annealing Algorithm on the Design of Satellite Orbits for Common-View Laser Time Transfer

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REMOTE SENSING 2024年第3期16卷 472页

作者： Xue, Han Zhang, Ziang Deng, Shiyu Mu, Liwei Fu, Jingqi Diao, Lingtian Chinese Acad Sci Changchun Observ Natl Astron Observ Changchun 130117 Peoples R China Univ Chinese Acad Sci Sch Astron & Space Beijing 100049 Peoples R China

Laser Time Transfer (LTT) has proven to be able to improve remote time transfer accuracy compared to microwave technology. The impact of satellite clock errors and atmospheric delays during LTT will be further reduced in the common-view mode. The challenge is presented as an optimization problem that is limited by satellite trajectories. This paper introduces an improved simulated annealing algorithm designed to maximize the common-view possibility among various station pairs within regional Satellite Laser Ranging (SLR) networks by optimizing satellite orbit trajectories. The study proposes a system model that integrates LTT principles with satellite visibility considerations. The simulated annealing algorithm is improved with new annealing strategies that incorporate control strategies, and modify the cooling function. Comparative simulation analyses demonstrate the effectiveness of the algorithm, resulting in a significant reduction in computation time by over 10 times. The optimized orbits exhibit common-view windows between 3.337 and 8.955 times longer than existing orbits. Further simulations are conducted to optimize the orbits, and common-view models are established for 45 pairs among 10 stations. The optimizations result in common-view times ranging from 6.183 to 60.633 min in the Asia-Pacific region and from 5.583 to 61.75 min in the Europe-to-Asia region. This can provide valuable references for designing satellite constellations.

关键词： laser time transfer trajectory optimization model simulated annealing algorithm common-view

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Bilevel trajectory optimization for Hypersonic Cruise Vehicle Using Bilevel Directed Search Domain

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JOURNAL OF SPACECRAFT AND ROCKETS 2021年第2期58卷 375-385页

作者： Wang, Kaiqiang Zhang, Bainan China Acad Space Technol Qian Xuesen Lab Space Technol Beijing 100094 Peoples R China China Acad Space Technol Beijing 100094 Peoples R China

For a returnable hypersonic cruise vehicle, the whole trajectory design is strongly coupled to the cruise state. To deal with the coupling relationship, a bilevel trajectory optimization problem is proposed in this paper. The upper level is for single-objective optimization of the whole trajectory, whereas the lower level is to conduct multiobjective optimization of the cruise flight. Based on the bilevel directed search domain (BDSD) algorithm, a bilevel trajectory optimization approach is proposed. Firstly, the dynamics model is established according to the coupling among the propulsion, aerodynamics, and trajectory. Then, the coupling relationships among different flight phases and those between the cruise trajectory and operate window of the scramjet are converted to optimization constraints. Thus, the highly coupled bilevel trajectory problem is transformed into a decoupled bilevel optimization problem, enabling the BDSD algorithm to solve the problem. Finally, the availability of the proposed approach is verified by the numerical results. Compared with another efficient method, the approach presented in this paper can drastically reduce the optimization time from tens or even hundreds of days to only about 8 days. Because of the high efficiency of the approach, the iterative trajectory design at the conceptual design stage is possible.

关键词： trajectory optimization model Aerodynamic Lift Scramjet Flight Phases Propellant Cruise Altitude Lift Coefficient Hypersonic Vehicles Flight Path Angle Earth

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Onboard Real-Time Generation of Launch Vehicle Abort Orbits

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2021年第8期44卷 1541-1549页

作者： Hao, Zeming Zhang, Ran Beihang Univ Sch Astronaut Beijing 100191 Peoples R China

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Robust Planning of Nonlinear Rendezvous with Uncertainty

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2017年第8期40卷 1954-1967页

作者： Yang, Zhen Luo, Ya-zhong Zhang, Jin Natl Univ Def Technol Coll Aerosp Sci & Engn Changsha 410073 Hunan Peoples R China

Practical uncertainties are not considered by optimal rendezvous trajectory designs proposed in many current studies. In this study, a robust optimization method for on-ground rendezvous trajectory design is proposed by considering the uncertainties and orbital replanning process. Two robust performance indices related to the final rendezvous errors and the total velocity increment v are first defined, then a multi-objective optimization model (including the minimum v and minimum rendezvous errors) is formulated. The unscented transformation method is used to efficiently compute the robust indices in optimization process, and a multi-objective, nondominated sorting genetic algorithm is employed to obtain a Pareto-optimal solution set. It is shown that the proposed approach can be used to design a rendezvous trajectory with the v and final rendezvous errors that are both robust against uncertainties. Furthermore, the proposed approach can identify the most preferable design space in which specific solutions for practical application of rendezvous control are selected.

关键词： Genetic Algorithm Sequential Quadratic Programming Elliptical Transfer Orbit Lambert Algorithm Robust Design Probability Density Functions Orbital Mechanics Target Spacecraft trajectory optimization model Apogee Altitude

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End-to-end optimization of chemical-electric orbit-raising missions

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JOURNAL OF SPACECRAFT AND ROCKETS 2004年第5期41卷 831-839页

作者： Oh, DY Randolph, T Kimbrel, S Martinez-Sanchez, M Space Syst Loral Palo Alto CA 94303 USA MIT Cambridge MA 02139 USA

A simple analytic multistage model is presented for combined chemical-electric orbit-raising missions. Expressions for transportation rates and optimum electric specific impulse are derived for two-stage, three-stage, variable-efficiency, and tank-limited missions of up to 100 days duration. The optimum electric specific impulse is shown to depend strongly on the specific impulse of the chemical thruster. A low-thrust-trajectory optimization model is combined with launch-vehicle performance data to derive end-to-end optimized three-dimensional chemical-electric orbit-raising profiles to geostationary orbit. Optimized profiles are derived for the Sea Launch, Ariane 4, Atlas V, Delta IV, and Proton launch vehicles. Optimum electric orbit-raising starting orbits and payload mass benefits are calculated for each vehicle. The mass benefit is shown to be between 6.1 and 7.6 kg/day with two SPT-140 thrusters, or up to 680 kg for 90 days of electric orbit raising. The optimized profiles are combined with the analytic model to a create simple parametric performance model describing multiple launch vehicles. The model is a good tool for system level analysis of electric orbit-raising missions and is shown to match calculated performance to within 13%.

关键词： Launch Vehicles trajectory optimization model Perigee Hall Thruster Exhaust Velocity Bipropellants Solar Electric Propulsion Satellites Rockets Electric Propulsion

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